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公开(公告)号：US11014648B2
公开(公告)日：2021-05-25
申请号：US15949232
申请日：2018-04-10
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Jeremy Phillip Taylor , Steven G. Hagerott , Philippe A. Ciholas
Abstract: An interconnected flight controller for an aircraft includes a mechanical linkage connecting a pilot interface with a copilot interface. When an input is provided to either of the pilot or copilot interfaces, coordinated motion is provided between them of a proportional magnitude and direction. A mechanical-disconnect element within the mechanical linkage is adapted to actuate mechanical decoupling between the pilot interface and the copilot interface. One or more sensors is coupled to the mechanical linkage to sense inputs and communicate the inputs to a fly-by-wire flight controller. An autopilot servo is coupled to the mechanical linkage for providing autopilot control or feedback and a force-feedback subsystem is connected to the mechanical linkage to simulate and apply an opposing force of aircraft control surfaces to the pilot interface and the copilot interface.
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公开(公告)号：US20240409202A1
公开(公告)日：2024-12-12
申请号：US18737131
申请日：2024-06-07
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Steven G. Hagerott
Abstract: A flight control system includes a first and second operator input means configured to receive a mechanical input from an operator and are connected to an artificial feel system and at least one sensor. The system includes a flight control computer (FCC) in data communication with the sensor, wherein the FCC receives a signal from the sensor in response to an input by the operator. The flight control system has first and second servo controllers in data communication with first and second servos, respectively, and the FCC. The servos are connected to control surfaces that, when moved, cause the aircraft to change attitude. The flight control system also includes a third and a fourth servo controller, the third and fourth servo controllers being in communication with the FCC and a dual-lane servo operably connected to a third control surface that, when moved, causes the aircraft to change attitude.
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公开(公告)号：US11299289B1
公开(公告)日：2022-04-12
申请号：US16431375
申请日：2019-06-04
Applicant: Textron Aviation Inc.
Inventor： Brian Anthony Derstein , Steven G. Hagerott
Abstract: A method for determining an aircraft angle-of-attack for aircraft stall protection includes providing an output signal from an angle-of-attack sensor and determining an initial angle-of-attack signal based on the output signal. The initial angle-of-attack signal is compensated to provide a pseudo angle-of-attack signal, and the pseudo angle-of-attack signal is mapped to a true angle-of-attack signal based on flight test data. The true angle-of-attack signal is compensated based on roll rate and sideslip or estimated sideslip to provide a compensated angle-of-attack. A complementary filter is applied that complements the compensated angle-of-attack signal with a higher frequency inertial angle-of-attack rate signal, calculated from aircraft inertial data, to provide an angle-of-attack complementary filter output. An angle-of-attack threshold for aircraft stall protection is determined based on one or more compensation parameters. Activation of aircraft stall protection is determined based on the angle-of-attack complementary filter output compared with the angle-of-attack threshold.
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公开(公告)号：US20180029690A1
公开(公告)日：2018-02-01
申请号：US15662773
申请日：2017-07-28
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott , Russell Peters , Stephen M. Eddy
CPC classification number: B64C9/00 , B64C5/02 , B64C5/10 , B64C9/14 , B64C13/40 , B64C2009/005 , B64D45/0005 , G05D1/0808
Abstract: An actuator hardover monitor for a control surface includes an actuator sensor for detecting an actuator position, a command model of an expected position of the actuator based on an input command, and a monitor to determine whether a difference between the actuator position and the expected position exceeds a threshold for a predetermined duration. A method of preventing a hardover event for a control surface includes commanding an actuator valve to a commanded position, determining continuously when the commanded position, or an actuator valve position, or a control-surface position, or a modeled actuator valve position exceeds a predetermined limit to provide an exceedance. The method may further include filtering a signal of the exceedance based on a time constant to provide a filtered exceedance, and switching to a backup control-surface actuator when the filtered exceedance exceeds the predetermined limit for a predetermined duration.
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公开(公告)号：US20240409203A1
公开(公告)日：2024-12-12
申请号：US18737093
申请日：2024-06-07
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Steven G. Hagerott
Abstract: A hybrid flight control system includes an operator input device having a force sensor and/or a position sensor. The operator input is connected to a first portion of the control surface via a mechanical linkage. The system includes an electro-mechanical actuator and an electro-mechanical actuator control system in data communication with the electro-mechanical actuator, as well as a flight control computing system in data communication with the operator input device and the electro-mechanical actuator control system. Upon receiving an input from an operator, the operator input device sends a signal to the flight control computing system. Upon receiving a signal from the operator input device, the flight control computing system sends a signal to the electro-mechanical actuator control system. Upon receiving a signal from the electro-mechanical actuator control system, the electro-mechanical actuator moves a second portion of the control surface according to a predetermined set of conditions.
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Patent Agency Ranking
公开(公告)号：US10976751B1
公开(公告)日：2021-04-13
申请号：US15828795
申请日：2017-12-01
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott , Russell Peters , Stephen M. Eddy
Abstract: A method for monitoring an oscillatory signal from an oscillating device includes filtering the oscillatory signal to within a desired frequency band to provide a filtered signal and extracting an amplitude from the filtered signal. The method further includes switching control of the oscillating device when the amplitude exceeds a predetermined amplitude requirement for a predetermined duration. An oscillatory signal monitor includes a first controller and a second controller each configured to independently control an oscillating device. An oscillatory signal based on a position of the oscillating device is filtered to a desired frequency band, and an amplitude is extracted from the filtered signal. A switch is provided for switching control of the oscillatory device from the first controller to the second controller when the amplitude exceeds a predetermined amplitude requirement for a predetermined duration.
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公开(公告)号：US10969796B2
公开(公告)日：2021-04-06
申请号：US16196485
申请日：2018-11-20
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott
Abstract: An autopilot nonlinear compensation method includes providing an autopilot command for executing an aircraft maneuver, determining a desired aerodynamic moment of the aircraft based on the autopilot command, providing a measured pilot interface position, determining a total aerodynamic moment of the aircraft based on the measured pilot interface position and the autopilot command in combination with the desired aerodynamic moment, determining a ratio of the desired aerodynamic moment to the total aerodynamic moment, and adjusting the autopilot command with a corrective command based on the ratio. The method may be used to stabilize autopilot control of an aircraft following nonlinear deployment of a control surface.
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公开(公告)号：US10960971B1
公开(公告)日：2021-03-30
申请号：US16127403
申请日：2018-09-11
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott , Philippe A. Ciholas
Abstract: An automatic yaw enhancement method for an aircraft having at least one propeller includes providing to a flight controller a pilot command from a pilot interface and avionic data for an airspeed, an angle of attack, and a thrust. A P-factor compensation is determined based on one or more of the airspeed, the angle of attack, and the thrust. A command to a trim device is determined based on a P-factor compensation. When a rudder bias persists, the command to the trim device is repeatedly updated until a rudder force input is nullified. The methods provide automatic pilot assistance for controlling yaw during asymmetric flight conditions and automatic turn coordination while allowing intentional side-slip for facilitating crosswind landings.
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公开(公告)号：US20190196509A1
公开(公告)日：2019-06-27
申请号：US16196485
申请日：2018-11-20
Applicant: Textron Aviation Inc.
Inventor： Steven G. Hagerott
IPC: G05D1/08
CPC classification number: G05D1/0825 , G05D1/085
Abstract: An autopilot nonlinear compensation method includes providing an autopilot command for executing an aircraft maneuver, determining a desired aerodynamic moment of the aircraft based on the autopilot command, providing a measured pilot interface position, determining a total aerodynamic moment of the aircraft based on the measured pilot interface position and the autopilot command in combination with the desired aerodynamic moment, determining a ratio of the desired aerodynamic moment to the total aerodynamic moment, and adjusting the autopilot command with a corrective command based on the ratio. The method may be used to stabilize autopilot control of an aircraft following nonlinear deployment of a control surface.
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公开(公告)号：US20180297691A1
公开(公告)日：2018-10-18
申请号：US15949232
申请日：2018-04-10
Applicant: Textron Aviation Inc.
Inventor： Stephen M. Eddy , Jeremy Phillip Taylor , Steven G. Hagerott , Philippe A. Ciholas
Abstract: An interconnected flight controller for an aircraft includes a mechanical linkage connecting a pilot interface with a copilot interface. When an input is provided to either of the pilot or copilot interfaces, coordinated motion is provided between them of a proportional magnitude and direction. A mechanical-disconnect element within the mechanical linkage is adapted to actuate mechanical decoupling between the pilot interface and the copilot interface. One or more sensors is coupled to the mechanical linkage to sense inputs and communicate the inputs to a fly-by-wire flight controller. An autopilot servo is coupled to the mechanical linkage for providing autopilot control or feedback and a force-feedback subsystem is connected to the mechanical linkage to simulate and apply an opposing force of aircraft control surfaces to the pilot interface and the copilot interface.
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